CN206900650U - A kind of vertical coaxial dual-rotor helicopter - Google Patents
A kind of vertical coaxial dual-rotor helicopter Download PDFInfo
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- CN206900650U CN206900650U CN201720389978.0U CN201720389978U CN206900650U CN 206900650 U CN206900650 U CN 206900650U CN 201720389978 U CN201720389978 U CN 201720389978U CN 206900650 U CN206900650 U CN 206900650U
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- bevel gear
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- coaxial dual
- vertical coaxial
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Abstract
Aircraft field is the utility model is related to, specially a kind of vertical coaxial dual-rotor helicopter.The vertical coaxial dual-rotor helicopter, the aircraft include base, fuel tank, engine and turn system are sequentially provided with above the base；The turn system is connected through reduction box with the engine；Support is additionally provided with above the base；Housing is provided with the fuel tank and the external engine, the housing is fixedly connected with the support；Actuation means and empennage are provided with the close housing of the support, the actuation means include manipulation arm, and the manipulation arm extends to first direction, and the empennage extends in a second direction, and the first direction is opposite direction with the second direction.Vertical coaxial dual-rotor helicopter provided by the utility model is compact-sized, light weight, floor space are small.
Description
Technical field
Aircraft field is the utility model is related to, specially a kind of vertical coaxial dual-rotor helicopter.
Background technology
Because existing manned vehicle uses sitting posture more, so as to form conventional airframe pattern, flown in conventional passenger
In device, engine connection reducer mode is as shown in figure 1, the lower bevel gear 53 is connected with interior rotor shaft 54, upper bevel gear 51
It is connected with outer rotor shaft 55, engine output shaft 30 is connected with the side bevel gear 52 of decelerator, and the side bevel gear 52 makes epicone
Gear 51 and the lower constant angular velocity of bevel gear 53 and rotation in opposite direction.Available engine arrangement is all by side in Fig. 1
Engine torque is passed on bevel gear 52, this kind of drive, makes manned vehicle not only sufficiently bulky, can also cause to fly
Its center line of the deviation of gravity center of device.Make aircraft flight less stable.
The content of the invention
In view of this, the utility model provides a kind of vertical coaxial dual-rotor helicopter, existing manned so as to solve
The shortcomings that aircraft volume is excessive, wide, Flight Vehicle Structure can be made compacter, compact.
In order to achieve the above object, the utility model mainly provides following technical scheme：
By a kind of vertical coaxial dual-rotor helicopter, the aircraft includes base, is sequentially provided with above the base
Fuel tank, engine and turn system；
The turn system is connected through reduction box with the engine；
Support is additionally provided with above the base；
Housing is provided with the fuel tank and the external engine, the housing is fixedly connected with the support；
Actuation means and empennage are provided with the close housing of the support, the actuation means include manipulation arm,
The manipulation arm extends to first direction, and the empennage extends in a second direction, the first direction and the second direction
For opposite direction.
In above-mentioned vertical coaxial dual-rotor helicopter, the turn system include upper rotor, lower rotor, interior rotor shaft,
Outer rotor shaft, propeller hub and pitch；The reduction box includes upper bevel gear, side bevel gear and lower bevel gear, the side bevel gear
Engaged respectively with the upper bevel gear and the lower bevel gear, the power output shaft of the engine is nibbled with the lower bevel gear
Close, the rotation direction of the lower bevel gear is identical with the rotation direction of the power output shaft of the engine；
The lower bevel gear is fixedly connected with the interior rotor shaft, and the upper bevel gear is fixed with the outer rotor shaft to be connected
Connect, the side bevel gear makes the upper bevel gear and the lower bevel gear constant angular velocity and rotation in opposite direction, the inward turning
Wing axle and the outer rotor shaft drive the upper rotor, the lower rotor constant speed, opposite direction and same axle center to rotate respectively.
In above-mentioned vertical coaxial dual-rotor helicopter,
The propeller hub is hingeless formula propeller hub, and the pitch is centre of sphere rotating disc type, and the outside of the blade is by glass fibre
Prepared by the material of prepreg, the structure that the inside packing material of the blade is formed is filled or shaped cellular for styling foam.
In above-mentioned vertical coaxial dual-rotor helicopter, the actuation means also include always away from throttle and course bar and week
Phase Adjustable length rod, the lifting being always used for away from throttle and course bar to the aircraft are controlled, and the cyclic is used
It is controlled in the heading to the aircraft.
In above-mentioned vertical coaxial dual-rotor helicopter, hold on the housing to first direction and be extended with head protection dress
Put.
In above-mentioned vertical coaxial dual-rotor helicopter, the head restraint includes display unit and transparent protection
Cover, the display unit electrically connects with the actuation means, and the display unit is ultra-thin soft screen liquid crystal display, the display
Unit is used to show flight performance parameter and flight environment of vehicle parameter.
In above-mentioned vertical coaxial dual-rotor helicopter, safe object wearing device is provided with below the head restraint；
And/or
Leg restraint is provided with the first direction of the support；And/or
Standing buffer is provided with the base.
In above-mentioned vertical coaxial dual-rotor helicopter, the reduction box includes clutch, and the clutch is centrifugal
Freewheel clutch.
In above-mentioned vertical coaxial dual-rotor helicopter, the housing is glass fibre material, and the base and support are
Aluminum alloy material.
In above-mentioned vertical coaxial dual-rotor helicopter, the actuation means also include round trip flight control system, the round trip flight
Control system includes intelligence system and automatic alarm system, wherein：
The intelligence system includes self-test unit, lock cell, automatic unit and the hovering unit of keeping in obscurity；
The automatic alarm system includes electricity alarm unit, barrier alarm unit, destination prompt unit, flight ginseng
Number alarm unit.
By above-mentioned technical proposal, the utility model proposes a kind of vertical coaxial dual-rotor helicopter at least have it is following
Advantage：
Vertical coaxial dual-rotor helicopter provided by the utility model is compact-sized, light weight, floor space are small.
Described above is only the general introduction of technical solutions of the utility model, in order to better understand skill of the present utility model
Art means, and being practiced according to the content of specification, with preferred embodiment of the present utility model and coordinate accompanying drawing detailed below
Describe in detail bright as after.
Brief description of the drawings
Fig. 1 is the structural representation of engine and Reducer connection in the prior art；
Fig. 2 is the structural representation of the utility model aircraft；
Fig. 3 is the front view of the utility model aircraft；
Fig. 4 is the internal structure schematic diagram of the utility model aircraft；
Fig. 5 is the engine of the utility model engine and the structural representation of Reducer connection.
Embodiment
Further to illustrate that the utility model is to reach the technological means and effect that predetermined goal of the invention taken, below
With reference to accompanying drawing and preferred embodiment, to according to the utility model proposes a kind of vertical coaxial dual-rotor helicopter specific implementation
Mode, structure, feature and its effect, describe in detail as after.In the following description, different " embodiment " or " embodiment " refers to
Be not necessarily the same embodiment.In addition, the special characteristic, structure or feature in one or more embodiments can be by any suitable
Form combines.
The vertical coaxial dual-rotor helicopter as shown in Figures 2 to 5, the aircraft include base 1, the base
1 top is sequentially provided with fuel tank 2, engine 3 and turn system 4；The turn system 4 connects through reduction box 5 and the engine 3
Connect；Support 6 is additionally provided with the top of the base 1；Housing 7, the shell are provided with outside the fuel tank 2 and the engine 3
Body 7 is fixedly connected with the support 6；Actuation means and empennage 9, the behaviour are provided with the close housing 7 of the support 6
Controlling device includes manipulation arm 8, and the manipulation arm 8 extends to first direction, and the empennage 9 extends in a second direction, described
First direction is opposite direction with the second direction.
That is, the fuel tank 2, engine 3 and turn system 4 are on the axis of the aircraft, the behaviour
Control device is placed in the front end of the aircraft, and the empennage 9 is placed in the rear end of the aircraft.Driver is described vertical in driving
During coaxial dual-rotor helicopter, figure is standing state.Fuel oil in the fuel tank 2 is delivered to by the transfer pump for fuel 20
In the engine 3.
Described turn system 4 for aircraft rotor under dynamic action, rotation produce rise, decline, advance, after
The system move back, turn left, turned right.The actuation means are the control aircraft flight state and the system of flight parameter.
In the present embodiment, the power output shaft of the engine 3 is directly nibbled to the interior rotor shaft 54 of the turn system 4
Close.The interior rotor shaft 54 is connected with the lower bevel gear of the reduction box 5, so as to drive the lower bevel gear to rotate.
In the present embodiment, the floor space very little of the base 1, the planimetric area of the housing 7 on the ground
Very little, the upper rotor, lower rotor form oar disk, a diameter of 3.2m of the oar disk when rotating.Stopping in the aircraft
When on the ground, the upper rotor and the lower rotor be arranged in parallel along course direction, so as to reduce the aircraft
Floor space.That is, aircraft provided by the utility model is very compact.
In the present embodiment, in order that the upper rotor and the lower rotor be arranged in parallel along course direction, institute can be passed through
Actuation means are stated when the aircraft arrives at, the state of the upper rotor and the lower rotor is adjusted, made
The upper rotor and the lower rotor are changed into above-mentioned state.
In the present embodiment, the floor space of the base 1 is about 2 ㎡.
As the embodiment that can be converted, any number that the diameter of the oar disk can be between 2.5~3.7m.Its
In, the diameter and rotating speed of the oar disk are inversely proportional, the diameter of the oar disk for 2.5m when, turn during the aircraft flight
Speed is 1100RPM, the diameter of the oar disk for 3.7 meters when, the rotating speed during aircraft flight is 700RPM.
In the present embodiment, a height of 2.45m of machine of the aircraft.It can ensure that driver can be carried out under standing state
Flight operation.
The upper rotor of the aircraft and lower rotor are coaxial anti-oars, and parallel in course direction is in a word, the upper rotor
It can be reversely rotated with lower rotor with constant speed, when rotating 180 °, again as a word.
In order to further save the aircraft stop when occupation of land control, can by the upper rotor and it is described under
Rotor is arranged to folding rotor.
Radiator 12 of the present utility model is arranged on the side of the direction second direction of the engine 3, that is,
Say, the radiator 12, so as to which, the radiator 12 is in radiating, will not cause driver towards the afterbody of the aircraft
Discomfort.
In the utility model, the fuel tank 2 is fixed on the base 1 by tank support.
Another embodiment of the present utility model provides a kind of vertical coaxial dual-rotor helicopter, further, described
Turn system 4 includes upper rotor, lower rotor, interior rotor shaft 54, outer rotor shaft 55, propeller hub and pitch；The reduction box 5 includes
Upper bevel gear 51, side bevel gear 52 and lower bevel gear 53, the side bevel gear 52 respectively with the upper bevel gear 51 and it is described under
Bevel gear 53 engages, and the power output shaft of the engine 3 engages with the lower bevel gear 53, and the lower bevel gear 53 turns
Dynamic direction is identical with the rotation direction of the power output shaft of the engine 3；The lower bevel gear 53 and the interior rotor shaft 54
It is fixedly connected, the upper bevel gear 51 is fixedly connected with the outer rotor shaft 55, and the side bevel gear 52 makes the upper bevel gear
51 and the constant angular velocity of lower bevel gear 53 and rotation in opposite direction, the interior rotor shaft 54 and the outer interior rotor shaft 55 divide
The upper rotor, the lower rotor constant speed, opposite direction and same axle center is not driven to rotate.The side bevel gear 52 plays transmission
And steering-effecting.The engine output shaft 30 is connected with the lower bevel gear 53.
In order to ensure in flight course, the head of driver can be effectively protected, and the aircraft is in the shell
The upper end of body 7 is extended with head restraint 70 to first direction.When in use, the head of driver can be placed in the head and protect
In protection unit 70.
The head restraint 70, the head restraint 70 and 7 turns of the housing are used in order to facilitate driver
Dynamic connection.
Certainly, can also be by the housing 7 as the embodiment that can be converted, the head restraint 70
Lower slider facilitates the wearing of driver to realize.
When it is implemented, the head restraint 70 includes display unit and transparent shield, the display unit with
The actuation means electrical connection, the display unit are used to show flight performance parameter and flight environment of vehicle parameter.It is described
Display unit is ultra-thin soft screen liquid crystal display, and the ultra-thin soft screen liquid crystal display is soft screen, and the soft screen is attached to transparent
On protective cover.The position of the ultra-thin soft screen liquid crystal display can be adjusted according to visual demand.
Wherein：The flight performance parameter includes flying speed, height, position, course line, instruction place, dump energy, electricity
Machine rotating speed, flight time, the parameter such as temperature in cabin.The flight environment of vehicle relevant parameter：Humidity, temperature, wind speed, air pressure, surrounding
The parameters such as environment.
The utility model additionally provides another embodiment, and in the present embodiment, the aircraft is protected on the head
The lower section of protection unit 70 is provided with safe object wearing device 71.The trunk of driver can be fixed by safe object wearing device 71, so as to
Enough ensure the high-altitude safe of driver.
The formula when it is implemented, the safe object wearing device 71 simply can also directly be collapsed using safety belt.
The utility model additionally provides another embodiment, and in the present embodiment, the safe object wearing device 71 includes
Air bag, the air bag are inflated in aircraft high-speed falling, so as to ensure the safety of driver.
The utility model additionally provides another embodiment, in the present embodiment, in the first direction of the support 6
It is provided with leg restraint.
The utility model additionally provides another embodiment, in the present embodiment, is provided with and stands on the base 1
Buffer 11.The standing buffer 11 includes spring and supporting surface, and the step of driver is placed on the supporting surface.Flight
For device during rapid increase, the spring can reduce overweight reaction to damage caused by driver's pin and leg.
As the embodiment that can be converted, the spring may be replaced by buffering flexible structure or other elasticity knots
Structure body, such as silica gel, air cushion etc..
Further, in the above-described embodiment, the actuation means also include always away from throttle and course bar and cycle
Adjustable length rod, the lifting being always used for away from throttle and course bar to the aircraft are controlled, and the cyclic is used for
The heading of the aircraft is controlled.The pitch for always passing through Synchronization Control rotor away from push-and-pull before and after throttle and course bar
(i.e. the angle of attack of blade) and throttle, make the lift of blade increase (diminution) simultaneously, and engine 3 increases (reduction) throttle, make interior dynamic
Power (aerodynamic force) and outer power (power of engine 3) are unified.Always away from throttle and course bar deflection by controlling lower blade
Displacement is uneven to make blade aerodynamic power appearance up and down, according to momentum balance principle, deflects aircraft course.
Feathering refers to that control stick controls pitch pull bar, makes pitch run-off the straight, and propeller pitch angle is according to the rotation of blade
Generating period change is put in indexing, because after phase, the factor such as oar disk lift asymmetry, makes oar card run-off the straight disk Tongfang
To inclination, aircraft flies towards inclined direction.
In the present embodiment, the control mode of actuation means uses Flying by wire.The manipulation arm 8 is provided with rocking bar.Its
In：Described is always the left hand rocking bar of driver away from throttle and course bar, and the left hand rocking bar is when preceding pushing away, on the aircraft
Rise；In post-tensioning, the aircraft declines the left hand rocking bar；For the left hand rocking bar at middle part, the aircraft altitude is not
Become (hovering or flat winged state)；During the left hand rocking bar Zola, course is turned left；When the left hand rocking bar right side pushes away, course is turned right
It is curved.
Human pilot is manipulated before and after left hand rocking bar by controlling, and is made always away from being carried out with throttle integration, when increasing pitch,
The throttle of engine 3 increases；When reducing pitch, the throttle of engine 3 reduces.
Left hand rocking bar is moved left and right to control the course displacement steering wheel of aircraft.Steering wheel rocking bar becomes lower blade pitch
Change, according to rotation momentum equilibrium principle, aircraft completes course turning flight.
The cyclic is the right hand rocking bar of driver, and the heading of aircraft can be controlled.Wherein：
During by being pushed away before the cyclic, the aircraft flies forward；During by the cyclic post-tensioning, the aircraft is backward
Move back；When the cyclic left side is pushed away, the aircraft is to moving to left；When the cyclic right side is pushed away, the aircraft
Move right.
Further, in the above-described embodiment, the turn system 4 includes pitch, propeller hub and two groups of asymmetric oars
Leaf, wherein：The propeller hub is hingeless formula propeller hub, and the pitch is centre of sphere rotating disc type, and the blade is by glass fibre prepreg
Epoxy resin material prepare, the structure that the paddle material is formed be styling foam fill or shape it is cellular, so as to
The blade is enough set to ensure very high intensity, and can substantially reduces the weight of the blade.The hingeless formula propeller hub
It is simple in construction, without flapping hinge and lead lag hinge, only pitch hinge.The upper rotor, waving for lower rotor rely on blade root with shimmy
Elasticity realize.Its structure is suitable for the aircraft of ultra-light-weight because blade is short, rotating speed bring it about soon wave with it is shimmy
Amplitude it is much smaller.By the setting of above-mentioned blade and above-mentioned propeller hub, the first half quality of the aircraft can be made to subtract significantly
Gently.
Upper pitch is connected with interior rotor shaft, can move up and down vertically；Lower pitch is connected with outer rotor shaft, it is impossible to
Move up and down.Centre of sphere formula rotating disk, which tilts, can carry out feathering simultaneously, always away from the manipulation of, course.The established angle angle of blade, lead to
The length of pitch-change-link is overregulated to realize.The blade is installed by screw thread roll adjustment.
Further, in the above-described embodiment, the reduction box 5 includes clutch, and the clutch is centrifugal super
More clutch.When the rotating speed of engine 3 reaches certain rotating speed, clutch is closed by the centrifugal force of centrifugal-block, and drive subtracts
The fast pinion rotation of case 5.Engine 3 is avoided to adjust the quality of clutch centrifugal-block because starting that load is excessive and difficulty in starting
To adjust the rotating speed of clutch generation.Engine 3 can drive rotor system to rotate by clutch, start when rotor rotating speed exceedes
During the rotating speed of machine 3, clutch surmounts, it is impossible to drives engine 3 to rotate and (typically occurs in when engine 3 stops working
It is existing).
When it is implemented, the speed reducing ratio of the decelerator is 3:1；The clutch main material is steel alloy；Rotor shaft
Rotating speed is 700RPM；The allowable rotating speed of clutch is 3000RPM；It is 300RPM that rotating speed is closed in the clutch centrifugation.
Further, in the above-described embodiment, the housing 7 is glass fibre material, and the base 1 and support 6 are
Aluminum alloy material.Glass fibre is much lower relative to carbon fiber price, and glass fibre will not shield radio (GPS) letter
Number.Base 1 and support 6 using the good and in light weight aluminum alloy materials of ductility, avoid landing, prominent wind load when produce and rush
Hit and be broken, " knife-like edge " will not be also produced when destruction and related system, component or driver are formed and injured.
The right-hand joystick controls two feathering steering wheels, and completing pitch by the push-and-pull of steering wheel rocking bar tilts,
Make blade generating period displacement, make lift that directional inclination occur, complete different directions flare maneuver.
Further, in the above-described embodiment, the actuation means also include round trip flight control system, the round trip flight control
System includes intelligence system and automatic alarm system, wherein：The intelligence system includes self-test unit, lock cell, covered automatically
Hinder unit and hovering unit；The automatic alarm system includes electricity alarm unit, barrier alarm unit, destination prompt list
Member, flight parameter alarm unit.
The self-test unit can carry out self-test to avionics system power-up condition.The lock cell can be to state of flight
Locked.The automatic unit that keeps in obscurity can be to being inputted, in by the signal of the collections such as camera, GPS, magnetic inertial navigation
Entreat analysis system analysis, then the regulation of automatic output signal or compensation control system, make aircraft voluntarily hide obstacle or
Prompting or warning driver complete corresponding operating.
The hovering unit, when can make the aircraft arrival instruction place, Automatic Approach to Hovering state, clearance is raised one's voice
Device sends the notice arrived at.
The intelligence system, additionally it is possible to which when ensureing that external environment condition is not suitable for taking off, be automatically locked turn system 4, does not perform
Take off task.
The electricity alarm unit, the aircraft can be made to carry out alarm when dump energy reaches critical point, such as
When electricity residue 20%, the electricity alarm unit sends alarm.
The destination prompt unit, instruction place can be reached in the aircraft and prompted.
Temperature, humidity, wind speed etc. do not possess takeoff condition before flight or piggyback pod temperature is too high, the flight parameter police
Declaration form member sends alarm.
When it is implemented, the rotor rotating speed of the turn system 4 is 700RPM；Maximum take-off weight be 250~
300Kg；Empty weight is 180~200Kg；Commercial load≤100Kg max level speeds：80Km/h；Economical cruise speed is
60Km/h；Rate of climb is 3m/s before maximum；Maximum climb altitude is 500m；Cruising time is 30min；Maximum, which is hovered, is highly
300m；The most long hovering time is 5min；The power of engine 3 is 80~100HP；Hundred inner oil consumption are 10L；Mailbox volume is 12L.
Further, the utility model additionally provides another embodiment, and the aircraft also includes illuminator, described
Illuminator includes course lamp unit and approach lighting unit.The course lamp unit is arranged on the front of manipulation arm 8,
The heading of the aircraft can be illuminated；The approach lighting unit is arranged on below the undercarriage, is used for
Aircraft lands are illuminated.
Further, the utility model additionally provides another embodiment, and the aircraft also includes hurricane globe, described to put
Fan housing is arranged on the front end of the aircraft, and for carrying out protection of leaking informaton to driver, the hurricane globe is transparent material system
Into the hurricane globe is rotatablely connected with the housing 7, and when driver goes on or off the plane, the hurricane globe turns to the housing 7
Top, to facilitate driver to go on or off the plane.
Further, the utility model additionally provides another embodiment, and the undercarriage is single-deck multiple spot landing structure.
The single-deck multiple spot landing structure is multiconductor damping device, and so as to reduce the generation of ground resonance, single-deck is used for equilibrium
Multiconductor, which contacts to earth, transmits load.
It is described above, only it is preferred embodiment of the present utility model, not the utility model is made any formal
Limitation, any simple modification, equivalent change and modification made to above example according to the technical essence of the utility model,
In the range of still falling within technical solutions of the utility model.
Claims (10)
- A kind of 1. vertical coaxial dual-rotor helicopter, it is characterised in thatThe aircraft includes base, and fuel tank, engine and turn system are sequentially provided with above the base；The turn system is connected through reduction box with the engine；Support is additionally provided with above the base；Housing is provided with the fuel tank and the external engine, the housing is fixedly connected with the support；Actuation means and empennage are provided with the close housing of the support, the actuation means include manipulation arm, described Manipulate arm to first direction to extend, the empennage extends in a second direction, and the first direction is phase with the second direction Anti- direction.
- 2. vertical coaxial dual-rotor helicopter according to claim 1, it is characterised in thatThe turn system includes upper rotor, lower rotor, interior rotor shaft, outer rotor shaft, propeller hub and pitch；The deceleration case and bag Bevel gear, side bevel gear and lower bevel gear are included, the side bevel gear nibbles with the upper bevel gear and the lower bevel gear respectively Close, the power output shaft of the engine is engaged with the lower bevel gear, and the rotation direction of the lower bevel gear is started with described The rotation direction of the power output shaft of machine is identical；The lower bevel gear is fixedly connected with the interior rotor shaft, and the upper bevel gear is fixedly connected with the outer rotor shaft, institute Stating side bevel gear makes the upper bevel gear and the lower bevel gear constant angular velocity and rotation in opposite direction, the interior rotor shaft and The outer rotor shaft drives the upper rotor, the lower rotor constant speed, opposite direction and same axle center to rotate respectively.
- 3. vertical coaxial dual-rotor helicopter according to claim 2, it is characterised in thatThe propeller hub is hingeless formula propeller hub, and the pitch is centre of sphere rotating disc type.
- 4. vertical coaxial dual-rotor helicopter according to claim 1, it is characterised in thatThe actuation means also include always away from throttle and course bar and cyclic, described to be always used for away from throttle and course bar Lifting and driftage to the aircraft are controlled, and the cyclic is used to carry out the heading of the aircraft Control.
- 5. vertical coaxial dual-rotor helicopter according to claim 1, it is characterised in thatHold on the housing to first direction and be extended with head restraint.
- 6. vertical coaxial dual-rotor helicopter according to claim 5, it is characterised in thatThe head restraint includes display unit and transparent shield, and the display unit is electrically connected with the actuation means Connect, the display unit is ultra-thin soft screen liquid crystal display, and the display unit is used for flight performance parameter and flight environment of vehicle Parameter is shown.
- 7. vertical coaxial dual-rotor helicopter according to claim 5, it is characterised in thatSafe object wearing device is provided with below the head restraint；And/orLeg restraint is provided with the first direction of the support；And/orStanding buffer is provided with the base.
- 8. vertical coaxial dual-rotor helicopter according to claim 1, it is characterised in thatThe reduction box includes clutch, and the clutch is centrifugal freewheel clutch.
- 9. vertical coaxial dual-rotor helicopter according to claim 1, it is characterised in thatThe housing is glass fibre material, and the base and support are aluminum alloy material.
- 10. vertical coaxial dual-rotor helicopter according to any one of claim 1 to 9, it is characterised in thatThe actuation means also include round trip flight control system, and the round trip flight control system includes intelligence system and automatic alarm system System, wherein：The intelligence system includes self-test unit, lock cell, automatic unit and the hovering unit of keeping in obscurity；The automatic alarm system includes electricity alarm unit, barrier alarm unit, destination prompt unit, flight parameter police Declaration form member.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720389978.0U CN206900650U (en) | 2017-04-14 | 2017-04-14 | A kind of vertical coaxial dual-rotor helicopter |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720389978.0U CN206900650U (en) | 2017-04-14 | 2017-04-14 | A kind of vertical coaxial dual-rotor helicopter |
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| Publication Number | Publication Date |
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| CN206900650U true CN206900650U (en) | 2018-01-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201720389978.0U Expired - Fee Related CN206900650U (en) | 2017-04-14 | 2017-04-14 | A kind of vertical coaxial dual-rotor helicopter |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114771824A (en) * | 2022-06-22 | 2022-07-22 | 沃飞长空科技(成都)有限公司 | Automatic folding device of screw, screw and aircraft |
-
2017
- 2017-04-14 CN CN201720389978.0U patent/CN206900650U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114771824A (en) * | 2022-06-22 | 2022-07-22 | 沃飞长空科技(成都)有限公司 | Automatic folding device of screw, screw and aircraft |
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